Supporting wing for flying machines



F. WENK ASUPPORTING WING FOR FLYINGVMACHINES Filed van. 17, 1922 f F. WENK SUPPORTING WING FDR FLYING MACHINES Filed Jan. 17, 1922 2 sheets-*sheet 2 Patented Dec. 9, 1924.

- 'I UNITE-D S'FKFlISl PATENT oFFicE.

FRIEDRICH WENIL'QF GOTTINGEN, GERMANY, AssIGNoE To EDWARD H. PALMER,

' TRUSTEE, oE'BosroN, MASSACHUSETTS.

SUPPORTING WINGl FOR FLYING MACHINES.

Application filed January17,.122. Serial No. 529,981.

and llth November, 1921, and of whichlthe A following is a specification.

This invention relates to flying machines of the airplaiietype, and consists more par# ticularly in improvements in the stabili'- zatio-n and control of suph machines.-

r reference to the'following description when taken in connection vwith the accompanying.

illustration of one specific'enibodiment therel of, while its scope will beiiiore particularly pointed out in the appended claims. In the dran-"ings,

. Fig. 1 is a view in plan looking from the underside and showing an airplane embodying one lforni of the invention, the fuselage and parts-other than the supporting wings 2 being omitted for sake of simplicity; -Fig..2 is a front elevation of the airplane shown in' Fig. 1: Fig. 3 is a side elevation ofthe saine airplane; 1

F'g. 4 is ai'eai elevation showing a second forni of airplane, the main wings of which are adapted to'autoinatieally turn -under the influence of lthe adjustableouter auxiliaryv wings;A Figq is a plan view of the airplane shown in Figli;

FigQ isv a side elevation of the same air-vl plane, the dotted lines showing the position of the wings when the machine is at rest; Fig. is a plan view of a third form of airplane, a portion only of the main wings of which are adjustable; and Fig. .8 is a longitudinal transverse -section taken on the line VIII-VIII in Fig'. 7.

4Referring to the forni of the invention shown in Figsl to'3 inclusive, an airplane is there sliown,'the main supporting wings i ofavliich comprise the 'parts la, 1b whichextend upwardly from the center to the sides to' present a- Vshape or positive dihedral' angle. In the directionof flight these Wings The invention vwill be best understood. by.

`arealso given each a positive angle of incidence of useful. amount. Such airplane also comprises thel outerauxiliary wing parts 2a, 2b, which are constructed to'serve as 4stabilizing and steering surfaces and are given each a negative angle of incidence. Preferably the main wings la, lb are provided with inclined lateral edges 4311, 3b, which in th'il'- -lustrative embodiment of the invention are inclined forwardly and inwardly `at an angle.

of about 10@ with the longitudinal medium plane of the airplane, so that .these edges ex tend 11i the direction -of the edge whirlsf iowing of from the main supporting wing The outer wing parts 2a, 2b each extends outwardly and rearwardly with its major portion lying ati-the rear of the lateral edges of the. adiacent main wing.

. wing part lies in a plane which intersects the Each outer main wing plane la, lb along the edges `3:33" at such an'in'elination as to give the desired negative angle of incidence' to the wing part 2%, or 2". This provides an outer stabilizing plane which, in the direction of flight, is negatively inclined with relation to the main wing and'is attachedl to the edges of the main wing by a portion bounded by oblique lateral edges. the attaching edge of the auxiliary' wing being oblique to the outer edge thereof. outer wing with a relatively small portion lying within `the influence of the edge wliirls from .the main wing and having its major apart a't the rear, of-the outer edges of the main'wing and outside of'the-influenceof such edgewhirls. -Thr0ugh this disposition of the auxiliary wings a high degree ofstability and control maybe had.;

VIn the forni of the invention shown in. 4Figs. 4to 6 inclusive, the parts of the airplane are essentially` the same as those already described and are designated by the same reference characters. In this construction, however, the 4main wings la, 1b are adapted to be turned about the axes 4, 4b which are indicated `by dotted lines. f The wings are thereby free to'adj ust themselves with reference to the body 5 under the in'- fluence of the airv forces'which act upon the auxiliary wing parts 2, 2". i The body 5 is held This provides an auxiliary in thedirection .ofv flight by a tail surface 6, the latter being somewhat loaded, and the axes 4a, 4b .being located ata point somemay be so adjusted by the action 'of the auxl iliary vwing-.parts QL. 9) that an automatic stabilization of, the machine may at'all times be obtained.l Furthermore, .the auxiliary wing parts 2a, 2b may be fastened 'by linksd or madeof elastic material so that, by elevating or lowering their loutermost points,

'they may be bent and their angle ofinclination thereby altered.l Any vof the usual controlling devices, `such as wires or similar yconnections, may. be provided lfor bending. the auxiliary wing parts at the will of the opi erato1 The auxiliary wing parts'may beso constructed that they are'norinally bent downward, but may be drawn upward through theuse of control wires, so .that

their negative angles of inclination may be increased.

In the drawings for purposes of illustration an oidinarfwarping gear is shown for 'adjusting the auxiliary wing parts-,such gear comprisingfor each wing the rod or link 10 having one endl connected tothe rear edgeof the auxiliary wing near its outer end, and the opposite end to'one larm of a bell-crank lever l1 pivotally connected on the struts.12 and '13. The remaining arm of the bell-'crankl lever is connected through the link 14 to the pivoted hand-'levers 15 arranged'at a convenient point with .reference -to the pilots position, sothat the latter by moving the two hand-levers 15 c'an'exercise. control di? rectly over tlie side wings and -tli-ereby f -directly over the'main wings."

By this means not only the lateral and longitudinal stabilization but valso thepfull control of the flying machine can be 'efected,'-' the lateral -control being provided byv op" positely adjusting the auxiliary wings, and.

control inan upward or downward direction being effected by adjust-ingboth .'mixilia'ry-v wings in the same direction. l

The links 14 extend 'substantially' along the direction of' tl 1eaxesft1, 1lb so that the main wings l, lb are not directly influenced by the governing-devices, the axes 4a, 4b be- ,ingfrsufiiciently rigid to sustainthe forces exerted by the links. The main wings are indirectly influenced, however, through the adjustment of the auxiliary wing parts to 'assist the side stabilizing and steering actions. f y

Instead'iof mounting the wings to turn aboutthe axes- 4?, 4b, they may be fastened or other resilient-devices'acting rigidly to the body and constructed elastically in such a way that, by the action of .the auxiliary wing parts, they are bent or warped to alter their angle lof incidence, such bending taking place mainly near the aux. iliary wing paits. Thestabilizing force in this .case is greater than where the wings turn as a whole about the axes 424.1, since 'the greatest alteration of lthe angle :of incidence takes place at the greatest distance from the median plane of 'the machine-where are air forces exert their greatest possible leverage with reference to the center of grav# ity. VVhetherthe main Wing is twisted or z turned, however/,a the elfective'angle of incidence o'f the wing is adjusted by the opera# tion of twisting or turning.

In the embodiment ofthe inventionshownin Figs.. 7. and 8 the same reference charac'- ters areusedto designate the main and auxiliary wing parts vand the same :general priii-l ciples'are controlled. In this'forin, however, to the vbody 5 there are rigidly attached two.

lforwardly and 'upwardly inclined girders 7 which comprise each a framework provided with a suitable covering and having a crosssectional outline-similar Ito the usual cross- -sectional outline of the front edges of a flying machine wing.'- These girders are preferably of such strength that theyare selfsupporting, that is ,to say, they are capable of sustaining the'l lhud without the use o-f external wires orv otrierreinforcements. 'Each girder 7 is provided with a pivot or articulation 4,' by means of. which the adjacent main wing part lis hinged'to the girder frame, permittingl the turning; adjustment i of the main wing with relationthereto.. The hinge Vattachmentl 4 is herein 'shownjas arranged at'the-frear lower ed'ge of the 'girderj the flowing air'moves very vslowlyvand there- `frame 7 so that it 'lies at theV point where fore causes' no unnecessary. air resistance@ i Atthe same-time the'o-verlapping portion 8 ofthe upper'main wing surface near' its forward edge is disposed 'concentrically withy v reference to 'the vpivot 4, being v given 1a.l cylindrical or -conical contour, which 'in all adjustedpositions of thewiiig entirely cov-* ers vthe-joint between the wing andthe-'girder b stantial-ly smooth, A rif thef upper curve of the' aerofoilandfwithoitLharmful .effect l frame and vprovides a uninterrupted profileff on the movement of air overthe saine.`

The overlapping portion` 8f is .preferably pressed into frictional contactwith thesurface of the wing part '.7, either `throiigh its own ,resiliency or by the use ofV auxiliary,

springs, and may be' utilized to vcheck or reduce the'vibratory movements of the main wing parts 1, or similar checking or .damping effects may behad. by the use of springs to the movements of the wings.

The action of the main wing part-S. l and A in' opposition the auxiliary wings 2 in respect to stabilization and control is substantially the same as in the twoI preceding forms, the outline of each auxiliary wing 2, however, being altered in that .it is somewhat more rounded `alongits leadingl edge and is thereby better vadapted for meeting the, air currents.

'In the direction of -llight thc main wing "l has its greatest breadth near its outer edge 3, this breadthdiminishing gradually to` ward the body 5. Near the body at 9 the width of the inain wing l decreases very rapidly. Theeflect, therefore of variationsl in the angle of incidence f-the entire main wing, due to adjustment of the wing Cpart 1 about the pivoti, is greatest -towar itsouter endand nearthe auxiliary Wing part 2, providing thereby a favorable stabilizing `effect through the. action of the auxiliary 'The described stabilizing and wings. The total breadth of the wing. effective for lift, however, and comprising the l surface of both the portions Tand l is suby. stantially thesame for 'the entire length of the wing, for the rigid girder portion 7 isenlarged toward the bodyin substantially 4the sameproportion vas the width of the adjustable wing part 1 decreases.

At the rear of the body 5, where the wing.

becomes sharply narrowed at 9,`there is providedA a. tail surface 6 having. such a :profile that it occupies approximately the space whichwould have' been occupied by the prolongation of the wing l were the latter proylonged to the body without its sharply narrowedftermination at the point 9. This tail adds to the lift Iof the machine approxi.- mately what is lost by the cutting away of thevmain` wing part l'near the body of the machine. rlhe tail surface 6-is constructed as. a load supporting surface, coacting with' the wings, sothat the lifting forces are appropriately distributed over the entire spread of the wings, the lift from the me-v dian plane of the machine toward the outer lateral edges of the wings following the elliptical curve of distribution.

steering devices have provedof great adaptability and effectiveness in connection with motorless gliders where merely the natural movements ofthe air are utilized, but they may also be used to advantage in connection with motor driven machines 0r by utilizingsmaller motors thanare` now customary.

While I have herein shown, and describedv for the purposes of illustration one or more Claims- An airplane having main supporting wingsarranged at a positive dihedral angle and auxiliary stabilizing wingsv attached to v4the outer ends of the main wing's-each auxiliary wing for normal flight `being inclined downwardly towards its tip with relationY to the adjoining main wing and its junction with the vmain wing being inclined forwardly and inwardly with relation to the median longitudinal planeof the airplane, the auxiliary outer wing `thereby presenting a negative angle -of attack .with relation to the angle Vof attack of the main wing and each auxiliary wing also extending rearwardly and. outwardly to a. substantial dista-nce away from the end of the adjoining mainwing to present a substantial portion at the rear thereof and outside the influence ofthe edge wh'irls therefrom whereby said aux? iliary wings may actas stabilizing surfaces.

2. An airplane having/.main 'supportingwings arranged 'at a positivedihedral angle, each main wing being adjustable to permit alterationin its angle of attack, and outer auxiliary stabilizingwings attached to the outer en ds of the main wings, Veach auxiliary wardly towards its tip with relation to the adjoining main wing and its junction with if' the main wing being inclined forwardly and inwardly with relation to the median loiigi* tudinal plane' of the'- airplane, the auxiliary outer wing thereby presenting 'a negative angle of attack with relation to the --angle of attack ofthe main winei and leach auxiliary wing also extendingv rearwardly and outwardly to a substantial distance away *fromy the end4 of the adjoining main wing to present asubstantial portion at the rea-r thereof.

-wing for normal light being inclined down.

andoutside the influence of the edge whirlsy y therefrom ywhereby said auxiliary wings may act as'stabilizing'surfaces.

, 3.' An airplane having-main supporting wings arranged at a positive dihedral'angle,

each main :wing being adjustable to permit'. alteration in its angle of attack and outer' auxiliary stabilizing wings pivotally attached to the outer ends of the main w1ngs,`- each auxiliary wing fornorinal flight beingv inclined downwardly. towards its vtips with relation to the adjoining main wing and its pivotal axis'being inclined 'forwardly and inwardly with relation to the medianlongitudinal plane of the airplane, the auxiliary wingcthereby presenting a negative angle of attack with relation to the angle of attack of the main wing and each auxiliary wing` also extendingrearwardly and outwardly to a substantial distance away' from the end of the adjoiningmain wing to `present a substantial portion at the rear'thereof and outslidefof the influence of the edge whirls therefromwheieby-saidauxiliary wings may act as stabilizing surfaces. i

im u

. wing also extending rearwardly and out? 4. An airplanehaving main supporting wings arranged '-at a positive dihedral an-A gle, each main' wing being adjustable to. permit alteration in its angle of attack and outer auxiliary stabilizing wings pivotally attached to the outer ends of the main wings, each auxiliary wing for normal flight being inclined downwardly towards its tips .with relation to the adjoining main, wing and its pivotal axis being inclined forwardly .and inwardly with relationto the median longitudinal plane of the airplane, the auxiliary wing thereby presenting a negativel angle of attack with relation to the angle of attack of the main wing andeach auxiliary wardlyto a substantial distance away from the end of the adjoining main wing to pi'esent a substantial portion at the rear thereof andoutside of the inliuence of the 'edge whirls therefromwhereby said auxiliary wings mayact as stabilizing surfaces, `and devices to control the angle Aof attack of each auxiliary wing withrelation to the angle of the main wing.

5. y'An airplane havingv main supporting @wings arrangedl at a *dihedral angle and outer auxiliary wings attached by obliquely out lateral edges to the lateral edges of the main wings, said auxiliary wings being extended outwardly and rearwardly with relation thereto, said main Vwings beingeaclt composed of a rigid forward portion and a rear portion pivoted tok said forward por-- tion on an axis4 transverse to the direction of flightfani'saidv auxiliary wings being each secured to said rear wing portion.

6. An airplane havi-nglmain supporting wings comprising each a rigid forward portion and a rear portion'pivoted to said' forlward portion to adjustably turn about an axistransverse to the direction of flight,

and an auxiliary outer Wing secured to eachrear portion and extending Aoutwardly and rearwardly therefrom;o

V7. An airplane -having' main supporting wings arranged at a dihedral angle and auxiliary wings attached by obliquely'cut lateral edges to the outer lateral edges of the main wings, said auxiliary wings being extended outwardly and rearwardly withv relation thereto,'said main wings being each compos'edof a rigid -forward portion'and a rear portion pivote'd to said forward portion von an axis transverse to the direction of ing extended outwardly and 'rearwardly flight, the latter being located at the under iide ofthe wing and in the 'region -wliere relatively slow airmovement takes place, and said auxiliary wings being each secured 8. An airplane having main supporting 'wings comprisingl each arigid forward portionand a rear portion pivoted to said 'for` ward portion rto adjustably turn abouty an axis transverse to the direction of flight, the

latter 'being' located at the under side of said wing and in the region where relatively slow air movement takes place, and -an auxiliary outer` wing secured to each rear pori tion and extending outwardly. and rear- 'wardly therefrom.'

9. An vairplane having main supporting wings arranged at .a dihedral angle and auxiliary wings attachedA by 4obliquely cut lateral edges to the outeiylateraledge's of the main w ings,.said auxiliary wings being extended' outwardly and rearwardly-z with relation'theret'o, said main wings being each tion on an axis transverse to the direction ,of flight, said rear portion decreasing in breadth from the outer lateral edges toward 4composed of a rigid forward portion and a rear portion pivoted to said forward porfrom its' lateral edge toward the median plane of the airplane, and an auxiliary outerv wing securedto each rear portion and -extending o utwardly and rearwardly therefrom. I

11. A n airplane having main *supporting wings arranged at adihedral angle and.

outer auxiliary wings attached by'obliquely cut lateral edges to the outer'edges of the main wings, said auxiliary wingsjbeing ex- I 'tended outwardly and rearwardly -witli relation thereto, said main -wings being eac-li composed of'a rigid forward portion and a rearportion pivoted tosaid forward portion on an axis transverse to thedirection of flight, said auxiliaryfwings beingeachsecured to said vrear wing portion` the surface of said rear wing portion being cut away toward the median planeof the apparatus, and a supporting tail surface' arranged to assist in Asupplying thelift lost by the absence lof the cut-away`part of the rear wing portion.

12. An airplanehaving main supporting wings arranged at a dihedral angle and outer 'auxiliary wings attached by obliquely out lateral edges to the outer lateral edges ofthe main wings, said auxiliary lwings betion and a rear portion pivoted tov said forward Aportion on an axis transverse to the direction of flight,- said auxiliary wings be-y ing secured to said rear wing portion, and the latter having provision foichecking its movement about the rigid forward portion..

13, An airplane having main supporting Wings comprising each a rigid forward porthe turning movement of said rear portion tion and a rear portion pivoted to said forabout the forward portion. f f ward portion tov adjustably turn about an In Witness whereof I affix my signature 10 axis transverse to the direction of flight, FRIEDRICH WENK.

l vl auxiliary outer Wings secured to each rear Witnesses:

portion and extending rearwardly andout- ERWIN WESINGER,

' wardly therefrom, and meansfor checking MARIA' Swann.' 

